Numerical Investigation of Flow Properties of Rotating Detonation Engines

다국어 초록 (Multilingual Abstract)

Based on Euler equations with one-step chemical reaction model, 3D numerical simulations of rotating detonation engine (RDE) are performed to investigate flow properties inside its combustor in detail. It is found that most of the flow field inside the combustor of RDE is under subsonic state. At the exit of the combustor, all detonation products exhaust subsonically. Thus, RDE needs a Laval tail nozzle to increase its performance. Near the areas of the detonation wave, the shock wave reflections, the interface between reactants and products, and the contact surface, the radial velocity is large; however, it’s still small and its effects on the performance of RDE can be ignored, compared with the corresponding circumferential and axial velocities. After the detonation wave, the circumferential velocity increases abruptly. While the oblique shock wave seeps, both the circumferential and axial velocities increase. At the exit of the combustor, the circumferential energy flux is about 20% of the total energy flux. This will cause energy loss and reduce RDE performance.